Intershaft seal assembly

ABSTRACT

An intershaft seal assembly comprises an annular seal ring disposed between a pair of annular runners connected to a hollow outer rotating shaft, and a surface of a co-axial inner rotating shaft. The centrifugal force resulting from rotation of the hollow outer rotating shaft effects engagement of the annular seal ring with the surface of the co-axial inner rotating shaft. The surface may be a radially-inward-facing surface of a retaining arm connected to the co-axial inner rotating shaft.

CROSS REFERENCE TO RELATED APPLICATIONS

This application is a continuation application of and claims priority toU.S. patent application Ser. No. 15/288,079 filed Oct. 7, 2016, now U.S.Pat. No. ######, which claims priority to U.S. Provisional PatentApplication No. 62/249,504 filed Nov. 2, 2015. The entireties of theseapplications are hereby incorporated by reference.

FIELD OF THE DISCLOSURE

The present disclosure relates generally to turbine machines, and morespecifically to intershaft seal assemblies used in gas turbine engines.

BACKGROUND

Intershaft seals and intershaft seal assemblies may be used to isolatespaces between shafts in turbine engines having co-axial shafts. In onecommon design, a first shaft connects a fan, a first stage compressor,and a second stage turbine while a second shaft connects a second stagecompressor and first stage turbine. The first shaft rotates at arelatively lower speed than the second shaft. The first and secondshafts are co-axial and may be either co- or counter-rotational. To beeffective, an intershaft seal must therefore isolate spaces between theshafts having potentially high differential rotational speeds, and thespaces may also have a potentially high differential pressure.

Intershaft seals are used in turbine engines which provide energy for awide range of uses. Examples of turbine engines include turbofan,turbojet, turboshaft, and turboprop engines. As just one example of thewide range of applications such engines are suitable for, gas turbineengines are used to provide propulsion to an aircraft.

A typical gas turbine engine comprises an inlet fan, a compressor, acombustor, a high-pressure turbine, and a low-pressure turbine. As oneexample of a typical dual-shaft gas turbine engine 50, FIG. 1illustrates a first shaft 20 which connects a fan 52, first stagecompressor 54, and second stage turbine 62. A second shaft 24 is hollowand is concentrically located around first shaft 20 and connects asecond stage compressor 56 with a first stage turbine 60. A combustor 58is disposed between second stage compressor 56 and first stage turbine60. First shaft 20 is radially inward from second shaft 24 and rotatesat a relatively lower speed. Intershaft seal assemblies 10 are used atleast at each axial terminus of outer shaft 24 to seal the spacesbetween the two concentric shafts 24, 20.

One design for an intershaft seal involves the use of a seal ring whichis sometimes referred to in the art as a piston ring. FIG. 2 illustratesa seal ring design for a prior art intershaft seal. Intershaft sealassembly 10 comprises a seal ring 12 in contact with an annularretaining arm 14. The seal ring 12 is disposed between a pair of runners16 (or retaining rings) which are spaced apart by a spacer 18 andcoupled to an inner shaft 20. Retaining arm 14 is coupled to a hollowouter shaft 22 and may be held in place by a retention member 24. Innershaft 20 and outer shaft 24 can be co- or counter-rotational. Sealassembly 10 serves to isolate high pressure fluid cavity 30 from a lowerpressure fluid cavity 32.

When inner shaft 20 and outer shaft 24 are not in motion, a slight gap(not shown) is present between seal ring 12 and retaining arm 14.However, once inner shaft 20 begins to rotate the centrifugal force fromrotation will move seal ring 12 radially outward and into contact withretaining arm 14. Seal ring 12 and runners 16 are initially eachrotating in the same direction and at the same rotational speed as innershaft 20. Once seal ring 12 is in contact with retaining arm 14, sealring 12 will begin rotating in the same direction and at substantiallythe same rotational speed as outer shaft 24.

FIG. 3 illustrates some of the forces acting on seal ring 12 duringoperation of the turbine engine (i.e. while inner shaft 20 and outershaft 24 are rotating). A relatively large centrifugal force(F_(centrifugal)) from rotation of the inner shaft 20 acts on seal ring12 in a radially outward direction, bringing seal ring 12 into contactwith retaining arm 14. An axial differential pressure force (F_(D/P))acts on seal ring 12 in the vicinity of the pressure boundary in adirection from high pressure fluid cavity 30 to low pressure fluidcavity 32. To form an effective seal, the centrifugal force must belarge enough to hold seal ring 12 in contact with retaining arm 14despite the axial force of differential pressure across the seal ring12.

Forces caused by relative lateral motion (F_(lateral movement)) betweenthe inner shaft 20 and outer shaft 24 act on seal ring 12 in a directioneither axially forward or axially aft. Finally a moment M, sometimesreferred to as ring tension, resists radial expansion during rotation ofseal ring 12.

The configuration described above with reference to FIGS. 2 and 3 hasdrawbacks. The difference in rotational speeds between inner shaft 20and outer shaft 24 creates high friction between seal ring 12 (rotatingwith outer shaft 24) and runners 16 (rotation with inner shaft 20)during transients when the forces caused by relative lateral movementbetween the shafts overcomes the centrifugal force effecting contactbetween seal ring 12 and the outer shaft retaining arm 14 thus forcingthe seal ring 12 to contact the forward or aft runner 16. This highfriction can cause excessive heat generation in the seal assembly 10 aswell as a high wear rate of seal ring 12.

Thus there is a need in the art for an effective intershaft sealassembly which is better suited to resist heat generation and wear ofthe seal ring.

BRIEF DESCRIPTION OF THE DRAWINGS

The following will be apparent from elements of the figures, which areprovided for illustrative purposes and are not necessarily to scale.

FIG. 1 is a schematic diagram of a typical dual-shaft gas turbineengine.

FIG. 2 is a depiction of a prior art intershaft seal assembly.

FIG. 3 is a depiction of some of the forces acting on a seal ring duringrotation of the shafts.

FIG. 4A is a depiction of an intershaft seal assembly in accordance withsome embodiments of the present disclosure.

FIG. 4B is a depiction of an intershaft seal assembly in accordance withsome embodiments of the present disclosure.

FIG. 4C is a depiction of an intershaft seal assembly in accordance withsome embodiments of the present disclosure.

FIG. 5 is a side profile view of the side surface of a runner inaccordance with some embodiments of the present disclosure.

While the present disclosure is susceptible to various modifications andalternative forms, specific embodiments have been shown by way ofexample in the drawings and will be described in detail herein. Itshould be understood, however, that the present disclosure is notintended to be limited to the particular forms disclosed. Rather, thepresent disclosure is to cover all modifications, equivalents, andalternatives falling within the spirit and scope of the disclosure asdefined by the appended claims.

DETAILED DESCRIPTION

For the purposes of promoting an understanding of the principles of thedisclosure, reference will now be made to a number of illustrativeembodiments illustrated in the drawings and specific language will beused to describe the same.

The present disclosure is directed to an intershaft seal assembly toovercome the aforementioned deficiencies. More specifically, thisdisclosure is directed to an intershaft seal assembly which reduces heatgeneration and seal right wear during operation. Detailed descriptionsof various embodiments of the disclosed intershaft seal assembly, andadditional advantages thereof, are presented below.

FIGS. 4A, 4B, and 4C are depictions of an intershaft seal assembly 100in accordance with some embodiments of the present disclosure. Theembodiments illustrated in FIGS. 4A and 4B are most suitable for sealingan axial end of an outer shaft, while the embodiment of FIG. 4C can beused for seals located apart from the outer shaft axial end.

Seal assembly 100 comprises an annular seal ring 102 engaged with aretaining arm 104. Seal ring 102 is positioned between a pair of axiallyspaced annular runners 106 which are connected to a first shaft 108.Retaining arm is connected to a second shaft 110. First shaft 108 ishollow, and second shaft 110 is positioned within and co-axial to firstshaft 108. Second shaft 110 can be referred to as the inner shaft, whilefirst shaft 108 can be referred to as the outer shaft. In someembodiments the second shaft 110 operates at a relatively lower speed(in rotations per minute) than the first shaft 108.

Annular seal ring 102 is positioned between a pair of annular runners106. Each runner 106 comprises an axially-facing, radially-extendingside surface 112. Runners 106 are arranged to create an opposing pair ofside surfaces 112, with seal ring 102 positioned between these opposingside faces 112. Runners 106 are connected to an outer surface 130 offirst shaft 108.

In some embodiments runners 106 are axially spaced apart by spacer 122.In some embodiments, such as that shown in FIG. 4A, spacer 122 isslightly larger in the axial dimension than seal ring 102 resulting in asmall gap 135 between seal ring 102 and runners 106.

In some embodiments a void 128 is present, bounded by seal ring 102,spacer 122, and side surfaces 112. In some embodiments the radialdimension of void 128 is greater than the radial distance betweenradially-inward facing surface 120 and a radially-outward facing surfaceof runner 106 to ensure that seal ring 102 does not “bottom out” orcontact spacer 122 as a result of radial motion between first shaft 108and second shaft 110.

Seal ring 102 has a radially-outward-facing surface 114. In someembodiments, seal ring 102 is segmented, or formed from overlapping sealring segments which together form an annular seal ring 102. In otherembodiments, seal ring 102 is a continuous annular ring. In someembodiments seal ring 102 is formed from a carbon-graphite material.Such material is low density, low friction, and relatively low modulusof elasticity. In other embodiments seal ring 102 is formed frommaterials having a higher stiffness such as carbon-carbon composite orceramic.

Retaining arm 104 extends radially outward from second shaft 110. Insome embodiments, retaining arm 104 may be “L” or “J”—shaped member witha first radially-outward extending section 116 and a secondaxially-extending section 118. Retaining arm 104 has a radially-inwardfacing surface 120 adapted for engagement with seal ring 102. In someembodiments the radially-inward facing surface 120 is disposed on secondaxially-extending section 118. In some embodiments radially-inwardfacing surface 120 is disposed on second shaft 110.

Seal assembly 100 divides a high pressure fluid cavity 124 from a lowpressure fluid cavity 126. When first shaft 108 and second shaft 110 arenot rotating, a small gap may be present between surface 114 of sealring 102 and surface 120 of retaining arm 104. As first shaft 108 beginsto rotate, runners 106, spacer 122, and seal ring 102 will initiallyrotate with first shaft 108. Centrifugal forces will act on seal ring102 in a radially outward direction to effect engagement between surface114 of seal ring 102 and surface 120 of retaining arm 104. Once surface114 is engaged with surface 120, seal ring 102 will begin to rotate withsecond shaft 110.

In some embodiments oil cooling and/or lubrication is provided to theengagement of surface 114 with surface 120, and/or to the engagement ofsurfaces 112 with seal ring 102.

In some embodiments, the axially-facing, radially-extending side surface112 of each runner 106 includes a plurality of hydrodynamic grooves 501.FIG. 5 is a side profile view of the side surface 112 of a runner 106 inaccordance with some embodiments of the present disclosure. As shown inFIG. 5, hydrodynamic grooves 501 are generally formed as arcuate-shaped,shallow slots along the side surface 112. Additional shapes anddimensions of hydrodynamic grooves 501 are contemplated. A direction ofrotation R is also illustrated. Hydrodynamic grooves 501 improve fluidflow around the seal ring 102 and minimize contact and friction betweenseal ring 102 and runner 106. In other embodiments, pads are providedbetween side surfaces 112 and seal ring 102.

As shown in FIG. 4C, the disclosed intershaft seal assembly 100 is notrequired to be used at the end of a first shaft 108. In someembodiments, runners 106 are connected to first shaft 108 via aconnecting arm 140 having a radially extending member 142 and an axiallyextending member 144. The axially extending member 144 has a radiallyoutward facing outer surface 130 to which runners 106 are connected.

Although the disclosed intershaft seal assembly 100 is discussed withreference to a two-shaft turbine engine, one of skill in the art wouldunderstand that applications of the disclosed assembly 100 are not solimited. For example, the disclosed assembly 100 can be applied toturbine engines having multiple stages and multiple (three or more)shafts. The disclosed assembly 100 can be used to isolate high and lowpressure spaces between each set of shafts.

The disclosed intershaft seal assemblies provide numerous advantagesover the prior art. In the disclosed embodiments, the seal ring 102 isbrought into contact with a retaining arm 104 that rotates at the speedof the second (inner) shaft 110. Since second shaft 110 typicallyoperates at a lower rotational speed than the first shaft 108, lesscentrifugal force is acting to engage seal ring 102 to retaining arm104. As a result, during lateral movements between the first shaft 108and second shaft 110, less heat is generated and there is lower wearduring operation. When first shaft 108 and second shaft 110 move axiallyrelative to one another, such axial movement is less likely to damageseal ring 102 as it is engaged with retaining arm 104 with less forcethan in the prior art. In other words, because the retaining arm 104 isconnected to the slower-speed second shaft 110, seal ring 102 is held toor engaged with retaining arm 104, and rotates with retaining arm 104,at a lower centrifugal force. This lower force is sufficient to isolatehigh pressure fluid cavity 124 from low pressure fluid cavity 126, butis reduced when compared to the prior art and therefore causes less wearand damage to seal ring 102. Initial studies of the disclosure suggestheat generation is lowered by 60% when compared to the prior art.Further reductions are attainable—up to 80% when compared to the priorart—when the disclosure is used with high-stiffness seal rings such asthose composed of silicon carbide.

The present disclosure further overcomes a root cause of excessive heatgeneration and wear of seal rings: that the radial loading generated bycentrifugal forces is much greater than what is required to overcomeaxial loading generated by differential pressure. In essence, prior artseals are sealed too tightly—radially loaded against a retaining arm toostrongly—and therefore excessive heat and wear can be caused by axialmovement between shafts and axial or radial distortions. Since radialloading is proportional to speed squared, engaging the seal ring withthe lower speed shaft's retaining arm can greatly reduce radial loadingand the consequent heat and wear.

Another factor that affects the amount of centrifugal force developed isrelated to the specific strength of the material used to fabricate theseal ring 102. Specific strength is Youngs modulus divided by thematerial density. A material with a high specific strength will havesome advantage in that the tension developed as the ring 102 expandsradially can help to counter some of the centrifugal force. This is arelatively smaller advantage than making the lower speed shaft the outerand the high speed shaft the inner. The ring tension that can bedeveloped is limited by the strength of the material and the initialradial gap between the outer diameter of the seal ring 102 and the innerdiameter of the outer shaft 108. Very high stiffness materials such asceramic tend to have limited tensile strengths compared with steel forexample. Designing with too large a gap will result in a dynamicinstability of the seal ring 102. In other words, instead of expandinguniformly the seal ring 102 will instead bounce around in the free spacebetween the two annular runners 106 and the two shafts 108, 110. Thiswill most likely result in damage or failure of the seal ring 102.

A review of likely candidate materials will reveal that almost allsuitable candidates are surprisingly similar in specific stiffness.Materials with low density tend to have low strength and materials withhigh strength tend to also have higher density. A potential way aroundthis problem is to remove material that adds weight, but does notcontribute substantially to stiffness of the piston ring. For a sealring 102 with a square or rectangular cross section, that implies thatthe material in the middle of the cross section should not be present.Using conventional fabrication techniques this implies that a seal ring102 cross section that looks like an inverted U would be superior to asolid square. Using additive manufacturing it may be possible to print aseal ring 102 with solid side walls, and a honeycomb like interior. Bothof these techniques essentially reduce the mass of the seal ring 102without significantly changing the stiffness of the cross section. Theresult effectively increases the specific stiffness of the seal ring 102and at the same time reduces the centrifugal loading.

The present application discloses one or more of the features recited inthe appended claims and/or the following features which, alone or in anycombination, may comprise patentable subject matter.

According to an aspect of the present disclosure, a seal assembly forsealing a high pressure fluid cavity from a low pressure fluid cavity,the cavities at least partially disposed between a hollow rotating shaftand a co-axial rotating shaft at least partially disposed within thehollow rotating shaft, the seal assembly comprises a pair of annularaxially-spaced runners attached to an outer surface of a first of theshafts, the runner having opposed axially-facing radially-extending sidesurfaces; an annular seal ring positioned between the runners, theannular seal ring having a radially-outward facing surface whereinrotation of the first shaft effects engagement of the radially-outwardfacing surface with a surface rotating with the second of the shafts;wherein the first of the shafts is the hollow rotating shaft.

In some embodiments the hollow rotating shaft and the co-axial rotatingshaft are adapted for counter-rotation. In some embodiments the hollowrotating shaft and the co-axial rotating shaft are adapted forco-rotation. In some embodiments the surface rotating with the second ofthe shafts is a radially-inward-facing surface of an annular retainingarm connected to the second shaft. In some embodiments the hollowrotating shaft is connected to at least one of a plurality of compressorblades or a plurality of turbine blades. In some embodiments theco-axial rotating shaft is connected to at least one of a plurality offan blades, a plurality of compressor blades, or a plurality of turbineblades. In some embodiments the seal assembly further comprises a spacerbetween the pair of axially-spaced runners. In some embodiments the sealassembly further comprises a plurality of hydrodynamic grooves formed inthe axially-facing radially-extending side surfaces of the pair ofaxially-spaced runners.

According to an aspect of the present disclosure, an intershaft sealassembly for sealing a high pressure cavity from a low pressure cavitybetween a first hollow shaft and a second shaft co-axial with anddisposed at least partially within the first hollow shaft, theintershaft seal assembly comprises a pair of axially-spaced annularrunners connected to the first hollow shaft; an annular seal ringdisposed between the runners, the annular seal ring having aradially-outward facing surface; a retaining arm connected to the secondshaft having a radially-inward facing surface; and wherein the rotationof the first hollow shaft effects engagement of the radially-outwardfacing surface of the annular seal ring with the radially-inward facingsurface of the retaining arm.

In some embodiments the retaining arm comprises a radially extendingmember and an axially-extending member, and wherein the radially-inwardfacing surface is disposed on the axially-extending member. In someembodiments the runners are connected to the first hollow shaft via aconnecting arm comprising a radially-extending member and anaxially-extending member, wherein the runners are connected to aradially-outward facing surface of the axially-extending member. In someembodiments the first hollow shaft is adapted to rotate at a higherrotational speed than the second shaft. In some embodiments the firsthollow shaft is adapted to counter-rotate the second shaft. In someembodiments the first hollow shaft is adapted to co-rotate the secondshaft. In some embodiments the annular seal ring further havingaxially-facing radially-extending side faces which are spaced fromaxially-facing radially-extending side faces of the runners. In someembodiments the intershaft seal assembly further comprises a spacerbetween the pair of axially-spaced runners. In some embodiments thefirst hollow shaft is connected to at least one of a plurality of bladesof a high pressure compressor stage or a plurality of blades of a highpressure turbine stage. In some embodiments the second shaft isconnected to at least one of a plurality of fan blades of a turbine fan,a plurality of blades of a low pressure compressor stage, or a pluralityof blades of a low pressure turbine stage. In some embodiments theintershaft seal assembly further comprises a plurality of hydrodynamicgrooves formed in the axially-facing radially-extending side surfaces ofthe pair of axially-spaced runners.

Although examples are illustrated and described herein, embodiments arenevertheless not limited to the details shown, since variousmodifications and structural changes may be made therein by those ofordinary skill within the scope and range of equivalents of the claims.

What is claimed is:
 1. A seal assembly for sealing a higher pressurefluid cavity from a lower pressure fluid cavity, the seal assemblycomprising: a hollow rotatable shaft having an outer surface; a co-axialrotatable shaft at least partially disposed within the hollow rotatableshaft, wherein the hollow rotatable shaft and the co-axial rotatableshaft at least partly define the higher pressure fluid cavity and thelower pressure fluid cavity; a pair of annular axially-spaced runnersattached to the outer surface of the hollow rotatable shaft, the runnershaving opposed axially-facing radially-extending side surfaces; anannular seal ring positioned between said runners, the annular seal ringhaving a radially-outward facing surface; and an annular retaining armattached to the co-axial rotatable shaft, the annular retaining armcomprising a first portion extending radially from the co-axialrotatable shaft and a second portion extending axially from the firstportion, the second portion defining a radially-inward facing surfacepositioned radially outward of a portion of the hollow rotatable shaftand the annular seal ring, wherein a radial height of the first portionof the retaining arm is greater than a radial height of the pair ofannular axially-spaced runners; wherein rotation of the hollow rotatableshaft effects engagement of said radially-outward facing surface of saidannular seal ring with said radially-inward facing surface of saidretaining arm.
 2. The seal assembly of claim 1 wherein said hollowrotatable shaft further comprises a connecting arm, the connecting armcomprising a radially-inward extending member and an axially extendingmember extending from the radially-inward extending member, and whereinsaid outer surface is a surface of the axially extending member.
 3. Theseal assembly of claim 2 wherein said first portion extends radiallyfrom the co-axial rotatable shaft at a first axial position, and whereinsaid co-axial rotatable shaft is axially disposed within the hollowrotatable shaft at said first axial position.
 4. The seal assembly ofclaim 3 wherein said second portion and said axially extending memberaxially overlap.
 5. The seal assembly of claim 1 wherein said hollowrotatable shaft and said co-axial rotatable shaft are adapted forcounter-rotation.
 6. The seal assembly of claim 1 wherein said hollowrotatable shaft and said co-axial rotatable shaft are adapted forco-rotation.
 7. The seal assembly of claim 1 wherein said hollowrotatable shaft is connected to at least one of a plurality ofcompressor blades or a plurality of turbine blades.
 8. The seal assemblyof claim 7 wherein said co-axial rotatable shaft is connected to atleast one of a plurality of fan blades, a plurality of compressorblades, or a plurality of turbine blades.
 9. The seal assembly of claim1 further comprising a spacer between said pair of axially-spacedrunners.
 10. The seal assembly of claim 1 further comprising a pluralityof hydrodynamic grooves formed in the axially-facing radially-extendingside surfaces of said pair of axially-spaced runners.
 11. An intershaftseal assembly comprising: a hollow rotatable shaft defining an axis ofrotation, the hollow rotatable shaft extending axially and having aradially inner shaft surface; a co-axial rotatable shaft at leastpartially disposed within the hollow rotatable shaft; a connecting armextending from said hollow rotatable shaft and having a radially outersurface; an annular seal ring carried by said connecting arm and havinga radially-outward facing seal surface, said annular seal ringpositioned between a pair of axially-spaced annular runners; a retainingarm connected to said co-axial rotatable shaft, the retaining armcomprising a radially-extending portion and an axially-extending portionhaving a radially-inward facing surface positioned radially outward ofsaid radially outer surface of said connecting arm, wherein a radialheight of the radially-extending portion of the retaining arm is greaterthan a radial height of the pair of axially-spaced annular runners; anda first fluid cavity and a second fluid cavity, each fluid cavity atleast partly defined between the radially inner shaft surface of thehollow rotatable shaft and the co-axial rotatable shaft; wherein therotation of said hollow rotatable shaft effects engagement of saidradially-outward facing surface of said annular seal ring with saidradially-inward facing surface of said retaining arm to thereby form aboundary between said first fluid cavity and said second fluid cavity.12. The intershaft seal assembly of claim 11 wherein said connecting armcomprises a radially-inward extending member and an axially extendingmember extending from the radially-inward extending member, and whereinsaid radially outer surface is a surface of the axially extendingmember.
 13. The intershaft seal assembly of claim 12 wherein saidannular seal ring is disposed between said runners at a first axialposition, and said radially-extending portion is connected to saidco-axial rotatable shaft at a second axial position displaced from thefirst axial position.
 14. The intershaft seal assembly of claim 13wherein said co-axial rotatable shaft is axially disposed within thehollow rotatable shaft at said second axial position.
 15. The intershaftseal assembly of claim 13 wherein said co-axial rotatable shaft is notaxially disposed within the hollow rotatable shaft at said second axialposition.
 16. The intershaft seal assembly of claim 11 wherein saidhollow rotatable shaft is adapted to rotate at a higher rotational speedthan said co-axial rotatable shaft.
 17. The intershaft seal assembly ofclaim 16 wherein said hollow rotatable shaft is adapted tocounter-rotate said co-axial rotatable shaft.
 18. The intershaft sealassembly of claim 16 wherein said hollow rotatable shaft is adapted toco-rotate said co-axial rotatable shaft.
 19. The intershaft sealassembly of claim 11 wherein said hollow rotatable shaft is connected toat least one of a plurality of blades of a high pressure compressorstage or a plurality of blades of a high pressure turbine stage.
 20. Theintershaft seal assembly of claim 11 wherein said co-axial rotatableshaft is connected to at least one of a plurality of fan blades of aturbine fan, a plurality of blades of a low pressure compressor stage,or a plurality of blades of a low pressure turbine stage.